CN106340207A - Flight Management Assembly For An Aircraft And Method For Monitoring Such An Assembly - Google Patents
Flight Management Assembly For An Aircraft And Method For Monitoring Such An Assembly Download PDFInfo
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- CN106340207A CN106340207A CN201610529202.4A CN201610529202A CN106340207A CN 106340207 A CN106340207 A CN 106340207A CN 201610529202 A CN201610529202 A CN 201610529202A CN 106340207 A CN106340207 A CN 106340207A
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- flight management
- management system
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- roll commands
- navigation
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- 238000012544 monitoring process Methods 0.000 title claims abstract description 15
- 238000000034 method Methods 0.000 title claims abstract description 13
- 230000004913 activation Effects 0.000 claims description 23
- 238000005096 rolling process Methods 0.000 claims description 8
- 230000004888 barrier function Effects 0.000 claims description 4
- 238000004364 calculation method Methods 0.000 abstract description 2
- 230000002950 deficient Effects 0.000 abstract 1
- 230000003213 activating effect Effects 0.000 description 3
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical group C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 2
- 125000004122 cyclic group Chemical group 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000007667 floating Methods 0.000 description 2
- 239000012634 fragment Substances 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 238000013475 authorization Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007717 exclusion Effects 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000003550 marker Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/0055—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements
- G05D1/0077—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements using redundant signals or controls
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- G—PHYSICS
- G08—SIGNALLING
- G08G—TRAFFIC CONTROL SYSTEMS
- G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
- G08G5/0047—Navigation or guidance aids for a single aircraft
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F11/00—Error detection; Error correction; Monitoring
- G06F11/07—Responding to the occurrence of a fault, e.g. fault tolerance
- G06F11/16—Error detection or correction of the data by redundancy in hardware
- G06F11/1629—Error detection by comparing the output of redundant processing systems
- G06F11/1641—Error detection by comparing the output of redundant processing systems where the comparison is not performed by the redundant processing components
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Theoretical Computer Science (AREA)
- Automation & Control Theory (AREA)
- Quality & Reliability (AREA)
- General Engineering & Computer Science (AREA)
- Traffic Control Systems (AREA)
- Navigation (AREA)
Abstract
A flight management assembly for an aircraft and method for monitoring such an assembly. The flight management assembly includes two guidance systems each provided with a flight management system, the flight management systems being independent, each of the flight management systems carrying out at least one calculation of roll commands for the aircraft, the flight management assembly also comprising a data generating unit, preferably forming part of a guidance computer, for calculating a roll command and a monitoring unit for carrying out a monitoring of the roll commands calculated by the two flight management systems and by the data generating unit in such a way as to be able to detect and identify a defective flight management system.
Description
Technical field
The present invention relates to a kind of for aircraft, especially for transporter flight management assembly, and one kind is used for
The method monitoring such flight management assembly.
Not exclusively, the present invention is more specifically applied to implement rnp ar (required navigation
Performance with authorization required) type need authorize required navigation performance operation flight
Device.These rnp ar area navigation on rnav (area navigation) type for the operation based on rnp (required
Navigation performance) type required navigation performance operation.These operations have in order to real on board the aircraft
Apply and require the characteristic of Special Empower.
The concept of known rnp corresponds to area navigation, and for area navigation, (on board the aircraft) with the addition of supervision and accuse
Alarm device, described device makes it possible to ensure that aircraft is maintained at around on the so-called rnp air route with reference to course line.In this air route
Outside there may be relief or other aircraft.The performance requirement of rnp action type is limited by rnp value, should
Rnp value represents the half width (in units of nm in the sea) around the air route with reference to course line, and aircraft should during operation
It is maintained in 95% time on this air route.Also define (around with reference to course line) second of the twice of its half a width of rnp value
Air route.The probability that aircraft deviates this second air route should be less than 10-7Per pilot time.
The concept of rnp ar operation also has more multiple constraint.In fact, rnp ar program is characterised by:
- rnp is worth:
It is less than or equal to 0.3nm and can be decreased to 0.1nm entering the nearly stage；And
Strictly less than 1nm and 0.1nm can also be decreased to when taking off and in overshoot flight phase；- Final Approach leg,
It can be curve；And
- barrier (mountain peak, traffic etc.), it may be located at respect to the twice rnp value with reference to course line, and for conventional
Rnp operation, there is provided with respect to the supplementary tolerance limit of barrier.
Directorate of Air is directed to rnp ar operation and defines targeted security grade tls (target level of safety)
So that the probability that aircraft deviates half-breadth air route d=2.rnp is not to be exceeded 10-7Per pilot time.
The present invention is applied to the flight management assembly including two navigation system, and each navigation system is equipped with fms
The flight management system of (flight management system) type is for implementing rnp ar operation.
Background technology
If aircraft should implement the required navigation performance operation needing to authorize of rnp ar type, carry-on machine
Load equipment and especially flight management assembly should be able to reach targeted security grade.
The purpose of the present invention is that have to make rnp ar program with until the ability to fly of rnp value of 0.1nm, and its
Take off, enter near and overshoot flight phase (under normal circumstances and under failure condition) and there is no any restriction.
However, for the aircraft with the mandate implementing such rnp ar program, especially allow for from leading
The error source that in boat loop, exclusion navigation command (or instruction) calculates, to avoid it for the possible shadow in aircraft course line
Ring.
In order to implement the operation of rnp 0.1 type, in the case that navigation instruction is lost or is malfunctioned, flight management assembly
The demanding class of " dangerous " type should be able to be followed.In addition, in the case of erroneous calculations is detected, aircraft should continue
Continue and navigated in automatic mode to be maintained on rnp air route.
Using the flight management assembly with two flight management systems, inconsistent between two flight management systems
In the case of, which is out of order to this assembly None- identified, and therefore aircraft cannot be navigated in automatic mode again.
Therefore, such aircraft is not authorized to implement such rnp ar operation.
Content of the invention
It is an object of the invention to making up this defect.
The present invention relates to a kind of flight management assembly for aircraft, this flight management assembly can be implemented mentioned above
And rnp ar operation, described flight management assembly includes two navigation system, and each navigation system is equipped with a tof tube
Reason system, described flight management system be independent and trustship on different devices, every in described flight management system
Individual be configured at least realize the calculating of the navigation instruction for aircraft in real time, it is horizontal that described navigation instruction includes at least one
Shake instruction, described flight management assembly also includes at least one monitor unit, described monitor unit be configured to realize for by
The supervision of the data that flight management system generates is so as to detect inconsistent.
According to the present invention:
Flight management assembly includes at least one data generating unit different from described flight management system, described number
It is configured to calculate in real time roll commands according to signal generating unit；And
Monitor unit is configured at least realize by two in the case that the data detecting flight management system is inconsistent
Comparison between roll commands that individual flight management system calculates and the roll commands being determined by data generating unit, so that
Can detect in the case of necessity and identify the out of order flight management system among described two flight management systems.
Therefore, because in view of by different from described flight management system and the data generating unit institute that will be described below
The roll commands calculating, monitor unit is capable of identify that the flight management system being out of order so as in trouble-free flight management
With the help of system, aircraft is navigated, this can allow for aircraft as described hereafter has with rnp type behaviour
Make the ability flown, and overcome aforesaid defect.
Preferably, described data generating unit is a part for the navigational computer of aircraft.
In a preferred embodiment, described monitor unit is configured to:
Calculate the roll commands being calculated by one of described first flight management system and by data generating unit institute
Calculate corresponding roll commands between the first difference and this first difference is compared with the first predetermined tolerance limit；
Calculate and calculated with by data generating unit by the horizontal instruction that another in described flight management system is calculated
Corresponding roll commands between the second difference and this second difference is compared with the first tolerance limit；And
Only when one of described first difference and the second difference are more than described first tolerance limit, just determine that corresponding rolling refers to
Order is inconsistent, and detects and identify that the flight management system calculating this inconsistent roll commands is to be out of order
's.
It is furthermore advantageous to:
Data generating unit is configured to follow rule to calculate rolling by the conventional air route of " following the tracks of (track) " type
Instruction,；And
Flight management system is configured to follow rule by the conventional horizontal course line of " hpath " type and to calculate navigation and refer to
Order, this navigation instruction includes at least one roll commands.
Advantageously, in order to calculate roll commands in real time, data generating unit is configured to one after the other then:
So-called activation leg in flight plan is identified according to aircraft current location, wherein should guide to this leg
Aircraft；
According to aircraft with respect to the position of described activation leg, the vector velocity direction of aircraft and activation leg
Direction, determine follow-up air route to be followed to find activation leg accurately；And
Based on for air route determined by current time, calculate corresponding roll commands.
It is furthermore advantageous to, the navigation of aircraft is according to by one of two navigation system i.e. so-called activation navigation system institute
The data providing is realizing, and flight management assembly includes switching device, and this switching device is configured to by monitoring
This out of order flight is included in the case that unit detects out of order flight management system and in the navigation system activating
In the case of management system, produce the switching of another activation making in described two navigation system.
In addition, in a particular implementation, flight management assembly includes be configured to realize identical supervision two
Monitor unit.
The invention still further relates to a kind of supervision method for monitoring flight management assembly as previously described, described tof tube
Reason assembly includes two navigation system, and equipped with flight management system, described flight management system is independent to each navigation system
And trustship in different equipment, each in described flight management system is configured at least realize leading for aircraft
The calculating of boat instruction, navigation instruction includes at least one roll commands, and described supervision method includes monitoring step, this supervision step
It is to realize the supervision for the data being generated by flight management system, enabling detection is inconsistent.
According to the present invention:
Described supervision method includes data genaration step, this data genaration step be by with described flight management system
At least one different data generating unit of uniting to calculate roll commands in real time；And
Monitor that step is to be flown by two at least in the case that the data detecting flight management system is inconsistent
The roll commands that management system calculates are compared with roll commands determined by data genaration step, enabling in necessary feelings
Detect and identify the out of order flight management system among described two flight management systems under condition.
Advantageously, monitor that step is:
Calculate and calculated with by data generating unit by the roll commands that one of described flight management system is calculated
Corresponding roll commands between the first difference, and this first difference is compared with the first predetermined tolerance limit；
Calculate and counted with by data generating unit by another roll commands being calculated in described flight management system
The second difference between the corresponding yaw instruction calculated, and this second difference is compared with the first predetermined tolerance limit；And
Only when one of described first difference and the second difference are more than described first tolerance limit, just determine that corresponding rolling refers to
Order is inconsistent, and detects and identify that the flight management system calculating this inconsistent roll commands is to be out of order
's.
The invention still further relates to a kind of aircraft, particularly transporter, it is equipped with flight management assembly as described above.
Brief description
Accompanying drawing makes it possible to be best understood by how realizing the present invention.In the drawings, identical reference marker refers to
Similar element.
Fig. 1 is the block diagram of a particular implementation of the flight management assembly of aircraft；
Fig. 2 to Fig. 4 shows that airline operation followed by aircraft, thus finding corresponding boat accurately for different types of navigation
Section, it makes the key character of the present invention become obvious.
Specific embodiment
Fig. 1 schematically show can illustrate the present invention for aircraft, especially for transporter tof tube
Reason assembly 1.
It is loaded onto this flight management assembly 1 carry-on and include two navigation system 2a and 2b, each navigation system
It is equipped with flight management system 3a and 3b of fms (flight management system) type.Two flight management systems
3a and 3b is independent and trustship is in different equipment (hardware).
The calculating being each configured to realize hereinafter explicitly pointing out in described flight management system 3a and 3b, especially
It is the calculating of the navigation instruction for aircraft, this navigation instruction includes roll commands.
According to being the so-called activation number that provided of navigation system by the only one in described two navigation system 2a and 2b
To realize the navigation of aircraft according to (particularly navigation instruction).
Described flight management assembly 1 also includes at least one monitor unit 4a, 4b, and described monitor unit 4a, 4b are configured
Become the supervision realized for the data being generated by flight management system 3a and 3b so as to detection is inconsistent.
Monitor unit 4a, 4b trustship is in the equipment (hardware) different from the equipment of two flight management system 3a and 3b of trustship
In.
According to the present invention, monitor unit 4a, 4b are configured to realize calculating for by two flight management system 3a and 3b
The supervision of the navigation instruction (or order) going out, to detect when necessary and to identify among flight management system 3a and 3b
That flight management system out of order, as described below.
Out of order flight management system refers to calculate and send the navigation instruction of at least one wrong (or incorrect)
Flight management system.
More properly, according to the present invention:
Flight management assembly 1 includes at least one data generating unit different from described flight management system 3a and 3b
5a, 5b, described data generating unit 5a, 5b is configured to calculate in real time roll commands；And
Monitor unit 4a, 4b be configured to realize the roll commands that calculated by two flight management system 3a and 3b with
The comparison between roll commands determined by data generating unit 5a, 5b, so as to detecting when necessary and identifying
Go out that flight management system out of order among described two flight management system 3a and 3b.
In one preferred embodiment, data generating unit 5a, 5b corresponds to the navigational computer of aircraft, or such as
A part of navigational computer 6a and 6b of aircraft is constituted shown in Fig. 1.Realize in modification one (unshowned), data is given birth to
Become unit 5a, 5b can also be arranged in the equipment in addition to navigational computer 6a and 6b.
Therefore, because considering by data genaration list different from described flight management system 3a and 3b and as mentioned below
The roll commands that first 5a and 5b is calculated, monitor unit 4a and 4b is capable of identify that the flight management system being out of order.
Monitor unit 4a and 4b is thus able to isolate out of order flight management system so that crew is capable of rnp
Operation.
Which, in order to the error in two flight management system 3a and 3b identified when necessary, monitor single
First 4a and 4b monitors the rolling order being received from flight management system 3a and 3b and data generating unit 5a and 5b and carries out
Relatively.
It can be envisaged that different comparisons in the framework of the present invention.
In a particular implementation, monitor unit 4a, 4b are configured to detect two flights by following operation
Inconsistent between management system 3a, 3b:
Calculate the roll commands being calculated by one of described flight management system and by described flight management system
Another corresponding roll commands calculating between difference；
This difference is compared with predetermined comparison tolerance limit；And
If this difference compares tolerance limit then it is assumed that data is inconsistent more than described.
In addition, in a preferred embodiment, monitor unit 4a, 4b are configured to:
Calculate the roll commands being calculated by one of described flight management system 3a and 3b and by data generating unit
The first difference between the corresponding roll commands that 5a, 5b are calculated, and by this first difference, (it is equal to predetermined tolerance limit
Or be not equal to aforesaid compare tolerance limit) be compared；
Calculate by another roll commands being calculated in described flight management system 3a and 3b and by data genaration list
The second difference between the corresponding roll commands that first 5a, 5b are calculated, and by this second difference and predetermined tolerance limit (its etc.
In or be not equal to aforesaid compare tolerance limit) be compared；And
If one of described first difference and the second difference (and only one) is more than described tolerance limit it is determined that corresponding
Roll commands be inconsistent and detect and identify that the flight management system calculating this inconsistent roll commands is
Fault.
As explicitly pointed out in one of later particular example, in order to calculate roll commands in real time, data is given birth to
Unit 5a, 5b is become to be configured to one after the other:
Current location according to aircraft identifies the so-called activation leg of flight plan, wherein should be to this activation leg
Vectored flight device；
According to aircraft with respect to the position of described activation leg, the velocity direction of aircraft and activation leg
Direction, determine follow-up air route to be followed to find activation leg accurately；And
Based on the air route determining for current time, calculate corresponding roll commands.
Flight management system 3a and 3b is configured to come by conventional " hpath " (following horizontal course line) type rule with normal
Calculate roll commands with mode.
Generally, the air route that " hpath " rule is calculated using the position pc based on aircraft ac and course line to be followed is by mistake
Difference ct (cross track, driftage away from) and air route angu-lar deviation tae (track angle error, yaw angle), such as
Shown in Fig. 2.
More properly:
Error of fairway ct is that (it is limited at two passing points for center of gravity and the follow-up course line of aircraft ac or leg lr
The distance between p1 and p2)；
The angular deviation tae in air route is the speed in the direction in one section of course line or leg (with respect to the north) and aircraft ac
Angle between degree direction vector；
Leg is that the basic fragment in flight plan (includes the junction side of passing point to be joined and these passing points
Formula)；And
One section of course line is fragment or the part (line segment, circular arc) in course line.
In addition, the leg of tf type is the leg lr such as connecting 2 points of p1 and p2 in flight plan in fig. 2 with straight line
Such leg.This tf type leg is defined by the coordinate in its direction, its length and terminal p2.With other kinds of institute
The floating leg of meaning is contrary, and this tf type leg (with respect to ground) is fixing, and wherein floating leg is by direction not
Terminal carrys out limited, axis (axe a intercepter) for example to be intercepted.
Generally, on board the aircraft, " hpath " rule is (to be followed by flight management by the conventional navigation pattern of nav type
The course line that system 3a, 3b is calculated based on the flight plan that crew is inputted) come used.
In addition, data generating unit 5a, 5b is therefore a part of navigational computer 6a, 6b, and it is configured to borrow
The conventional rule of " tracking " (air route is followed) type is helped to calculate roll commands.
" tracking " rule is to be passed through by fcu (flight control unit, flight control units) type by crew
Frequently-used data input block (selection navigation pattern) that input desired air route value and manually used.
In the case that crew's selected navigation pattern is nav (automatically following course line), two flight management systems
System 3a and 3b uses " hpath " rule.
" tracking " rule thus be crew can select in addition to nav pattern (selecting) navigational computer 6a,
One of pattern of 6b, it is unrelated with the course line being generated by flight management system 3a, 3b.
" tracking " rule can be by the velocity direction controlling of aircraft on (with respect to northern) desired direction.
As explanation, if for example wanting to make aircraft east fly, " tracking " rule can be used with by the speed of aircraft
Direction vector controls on 90 degree of course.
Limit and the navigation channel deviation that is current air route (the course line tc in Fig. 3) of aircraft and target course (leg
Li " tracking " rule of the proportional roll commands of the difference between) is simple, and it is made with by flight management system
" hpath " type rule is unrelated.
" tracking " rule generally should can use on board the aircraft, and therefore its purpose has been only that the speed of aircraft
Vector axle controls on target course, as passed through shown in target ti of air route in Fig. 3.Therefore, the original state according to aircraft, flies
Row course line changes, and this makes to follow fixing leg, i.e. current course line leg in flight plan.Aircraft therefore can weigh
Newly return on the course line tc parallel with leg li without this leg of convergence.
As shown in figure 4, in order to find leg lr accurately, flight management assembly 1 calculates to be followed follow-up air route t1, t2, thus
This leg lr can be found accurately.These air routes t1, t2 be sent to navigational computer 6a, 6b with ask its with " tracking " rule come with
With these air routes.
Before point p3, the air route followed is t1, and after point p3, the air route followed is t2+ ε.Wherein ε depends on
In path-keeping error ct.ε is a little angle step to guarantee that aircraft ac levels off to leg lr exactly." tracking " rule is not
Consider the velocity direction of aircraft.In order to avoid t2 followed by aircraft parallel to leg, when aircraft does not have not strictly
In the case of being on leg, calculate slightly different instruction so that this leg of aircraft convergence.Configuration example such as data genaration
So-called " calculating of trace command and sequence " function of a part for module 5a, 5b, according to position, the aircraft ac of aircraft ac
Velocity direction and leg lr to be found accurately direction calculating these information.
Consider as follows apart from d: it corresponds to above-mentioned functions control and goes to the second instruction (air route from the first instruction (air route t1)
T2 the distance) passed through.This depends on the speed of aircraft and the difference of t1 and t2 value apart from d.
For example constitute the algorithm of a data generating unit 5a, 5b part, the parameter according to aircraft ac is calculating t1 and t2
Air route value, and appropriate opportunity be sent to navigational computer 6a, 6b so that navigational computer 6a, 6b " with
Track " rule calculates the roll commands that can take aircraft on the lr of leg.
The algorithm using by this is depending on the type of considered leg:
For tf leg, (the reason for comfort of passenger, it is equal to and is limited to be equal to the angle of nominal rolling apart from d
25 degree of course change) turning radius with during rolling with aircraft speed passed through apart from sum, wherein this rolling
All project on the normal in leg direction；
For other kinds of leg, in the case of being navigated by " hpath " rule, algorithm is according to closest
The flight state of aircraft performance and time generate air route instruction summary.
In a particular implementation, the enforcement of this example is as follows:
Two flight management system 3a and 3b extract rnp-ar program from data base and are inserted in flight plan.
Each in described flight management system 3a and 3b is passed through to this flight plan calculating cyclic redundancy check code crc (cyclic
Redundancy check), and flight plan and crc code be sent to by (activation system) so-called " leading " flight management system
Monitor unit 4a, 4b, and the second flight management system only sends the crc code of the flight plan that it calculates.Monitor unit 4a, 4b
Two crc codes are compared, in the case that two crc code-phase are same, monitor unit 4a, 4b make to connect from main flight management system
The flight plan received comes into force；
Monitor unit 4a, 4b (or data generating unit 5a, 5b) are according to the position of aircraft to the boat in flight plan
Section is ranked up, and it is to identify in the leg sequence of flight plan should be to the leg of its vectored flight device；
According to aircraft with respect to position, the velocity direction of aircraft and the side activating leg activating leg
To " calculating of trace command and sequence " function determines follow-up air route to be followed to find leg accurately, as shown in Figure 4.
In preferred implementation as shown in Figure 1, flight management assembly 1 includes being configured to realize same supervision
Two monitor unit 4a and 4b.This makes it possible to one of these monitor units 4a and 4b situation that is out of order in rnp operates
Under, remain able to detect out of order flight management system 3a or 3b when necessary, and thereby, it is ensured that the type
The required integrity of rnp operation.
In addition, flight management assembly 1 includes switching device, this switching device is configured to by monitor unit 4a, 4b
In the case of detecting out of order flight management system (it is, for example, flight management system 3a) and in activation navigation system
Be including the navigation system (it is navigation system 2a in this example) of this out of order flight management system in the case of, produce
Switching, this switching is to make another activation in described two navigation system 2a and 2b (be navigation system in this example
2b).
In a particular implementation, switching device includes (unshowned) button, and this button is arranged on driver's
Position and enable crew's Non-follow control switch.In addition, realizing in modification at one, control device includes at least one
Individual control unit 8a, 8b, this control unit be arranged in navigational computer 6a and 6b and according to the monitored state receiving Lai
Realize switching.
As shown in figure 1, each navigation system 2a, 2b includes information source assembly 7a, 7b, described information come source component 7a,
7b particularly including conventional sensors for determine (measurement, calculate ...) and aircraft state (position, speed ...) and
The related parameter value of its environment (temperature ...).Assembly 7a, 7b can also include ndb (navigation data base) type
Navigational route database, it is particularly including the definition of the rnp-ar program being used.
These values and information be provided to by connection l1a, l1b of assembly 7a, 7b corresponding flight management system 3a,
3b (" corresponding " refers to that it constitutes a part for same navigation system 2a, 2b).
Generally, each in flight management system 3a and 3b is in particular upon the value being received from corresponding assembly 7a, 7b
With information carrys out the gap between the position of calculating aircraft, the course line of aircraft, the position of aircraft and course line, and navigation refers to
Order particularly roll commands are with by the position control of aircraft on-course.
Flight management assembly 1 therefore also includes data generating unit 5a, 5b, and it is horizontal that data generating unit 5a, 5b calculates the 3rd
Shake instruction.This data generating unit 5a, 5b is used as the 3rd Data Source to be compared in monitor unit 4a, 4b and to decide by vote.
This data generating unit 5a, 5b only realizes pointed operation and calculating and not corresponding with (the 3rd) flight management system.
Monitor unit 4a respectively via connect l2a, l3b and l4a from flight management system 3a, flight management system 3b and
Data generating unit 5a receive information, and corresponding flight management system 3a can be provided information to via connecting l5a.Prison
Via connecting l6a, the monitoring result implemented can also be provided to navigational computer 6a depending on unit 4a.
In a similar manner, monitor unit 4b respectively via connect l2a, l3b and l4b from flight management system 3a, flight
Management system 3b and data generating unit 5b receive information, and can provide information to fly accordingly via connecting l5b
Row management system 3b.Monitor unit 4b can also provide the monitoring result implemented to navigational computer 6b via connecting l6b.
As shown in figure 1, each in two navigation system 2a and 2b in flight management assembly 1 includes fg (flight
Guidance, flight navigation) type navigational computer 6a, 6b.Described navigational computer one of 6a, 6b, that is, activate navigation system
Navigational computer, manipulate for the conventional servo control mechanism managing aircraft with according to navigation instruction vectored flight device.In order to grasp
Vertical servo control mechanism and vectored flight device and the logic that makes a choice between navigational computer 6a and navigational computer 6b are permissible
Implement at navigational computer 6a and 6b in a usual manner via conventional communication unit 8a and 8b.
The supervision work implemented by flight management assembly 1 hereinafter will be clearly stated.
Detect between the data being generated by flight management system 3a and 3b inconsistent in the case of, by monitor unit
The supervision that 4a and 4b is implemented is based on the analysis to roll commands.
For this reason, each in monitor unit 4a and 4b one after the other implements the steps of:
E1 the roll commands being calculated by one of described flight management system) are calculated and by data generating unit institute
The first difference between the corresponding roll commands calculating, and this first difference is compared with the first predetermined tolerance limit；
E2) calculate by another roll commands being calculated in described flight management system and by data generating unit
The second difference between the corresponding roll commands being calculated, and this second difference is compared with the first predetermined tolerance limit；
And
E3) only in the case that one of described first difference and the second difference are more than described first tolerance limit, just determine
Corresponding roll commands are inconsistent and detect and identify the flight management system calculating this inconsistent navigation instruction
System is out of order.
Therefore, a kind of method for monitoring the navigation instruction from flight management system 3a and 3b output, the method are obtained
Quickly, simply, cheaply and effective.
Flight management assembly 1 as above therefore have based on two flight management system 3a and 3b and (especially by
Monitor unit 4a and 4b is implemented) roll commands monitor structure, so as to implement rnp 0.1 type operation.
This flight management assembly 1 hence allows to:
Obtain quick response time；
(in the case that roll commands calculate and make mistakes) identifies out of order flight management system so that this goes out if necessary
The flight management system of fault lost efficacy, and followed the work of not out of order flight management system, and if possible then will
Out of order flight management system re-synchronization is in not out of order flight management system；And
Avoid have to costly and complicated the 3rd flight management system (for use as the 3rd voting source) is installed.
It should be pointed out that the air route that calculated using position based on aircraft and course line to be followed of " hpath " rule
Differential seat angle away from Error of fairway value.If it is intended to using the 3rd " hpath " rule for function for monitoring, then must be based on from two
The reinforcement flight plan that flight management system is received, to calculate course line, receives position of aircraft to calculate Error of fairway and air route
Differential seat angle is away from this will revert to the 3rd flight management system using simplification completely.Therefore, by using navigational computer
More simply to calculate the 3rd navigation instruction, (this calculating is based only upon flight plan it is not necessary to calculate course line to " tracking " rule, in addition
" tracking " rule generally can use on board the aircraft), in the case that two flight management systems send inconsistent instruction,
Flight management assembly can identify in this two flight management systems which make mistakes.
Claims (10)
1. a kind of flight management assembly for aircraft, described flight management assembly (1) include two navigation system (2a,
2b), each navigation system is equipped with flight management system (3a, 3b), described flight management system (3a, 3b) be independent simultaneously
And trustship is in different equipment, each in described flight management system (3a, 3b) is configured at least realize in real time pin
Calculating to the navigation instruction of aircraft (ac), described navigation instruction includes at least one roll commands, described flight management group
Part (1) also includes at least one monitor unit (4a, 4b), and described monitor unit (4a, 4b) is configured to realize for by described
The supervision of the data that flight management system (3a, 3b) is generated, so as to detecting that at least one is inconsistent, its feature exists
In:
- described flight management assembly (1) includes at least one data genaration lists different with described flight management system (3a, 3b)
First (5a, 5b), described data generating unit is configured to calculate in real time roll commands；And
- described monitor unit (4a, 4b) is configured at least differ in the data detecting described flight management system (3a, 3b)
In the case of cause, realize the roll commands that calculated by two flight management systems (3a, 3b) with by described data generating unit
Comparison between roll commands determined by (5a, 5b), so as to detecting when necessary and identifying described two flying
That flight management system out of order among row management system (3a, 3b).
2. flight management assembly according to claim 1 is it is characterised in that described monitor unit (4a, 4b) is configured to:
- calculate in the roll commands being calculated by one of described flight management system (3a) and by described data generating unit
The first difference between the corresponding rolling order that (5a, 5b) is calculated, and by this first difference and the first predetermined tolerance limit
It is compared；
- calculate and given birth to by described data by another roll commands being calculated in described flight management system (3a, 3b)
Become the second difference between unit (5a, 5b) the corresponding roll commands that calculated, and by this second difference and described first
Tolerance limit is compared；
- only when one of described first difference and described second difference are more than described first tolerance limit, just determine horizontal accordingly
It is inconsistent for shaking instruction, and detects and identify that the flight management system calculating this inconsistent roll commands is event
Barrier.
3. flight management assembly according to claim 1 and 2 is it is characterised in that described data generating unit (5a, 5b) structure
Become a part for the navigational computer (6a, 6b) of described aircraft (ac).
4. according to flight management assembly in any one of the preceding claims wherein it is characterised in that:
- described data generating unit (5a, 5b) is configured to follow rule to calculate described roll commands by air route；And
- described flight management system (3a, 3b) is configured to follow rule and to calculate by horizontal course line comprise at least one horizontal stroke
Shake the navigation instruction of instruction.
5. according to flight management assembly in any one of the preceding claims wherein it is characterised in that in order to calculate institute in real time
State roll commands, described data generating unit (5a, 5b) is configured to one after the other:
- so-called activation leg (lr) in described flight plan is identified according to the current location (pc) of described aircraft (ac),
Wherein described aircraft (ac) should be guided to this activation leg；
- according to the velocity of the position with respect to described activation leg (lr) for the described aircraft (ac), described aircraft (ac)
Direction and the direction of described activation leg (lr), determine follow-up air route (t1, t2) to be followed to find described activation leg accurately
(lr)；And
- based on the air route determining for current time, calculate corresponding roll commands.
6. according to flight management assembly in any one of the preceding claims wherein, the navigation of described aircraft (ac) be according to by
One of two navigation system (2a, 2b) are the so-called activation data that provided of navigation system to be realized,
It is characterized in that, it includes switching device (8a, 8b), and described switching device (8a, 8b) is configured to single by monitoring
It is to go out event including this in the case that first (4a, 4b) detects out of order flight management system and in described activation navigation system
In the case of that navigation system of flight management system of barrier, produce switching, this switching is to make described two navigation system
Another activation in (2a, 2b).
7. according to flight management assembly in any one of the preceding claims wherein it is characterised in that it includes being configured to reality
Two monitor units (4a, 4b) that existing identical monitors.
8. a kind of method for being monitored to the flight management assembly of aircraft, described flight management assembly (1) includes two
Individual navigation system (2a, 2b), each navigation system is equipped with flight management system (3a, 3b), described flight management system
(3a, 3b) is independent and trustship is in different equipment, and each in described flight management system (3a, 3b) is configured to
At least realize the calculating of the navigation instruction for described aircraft (ac), described navigation instruction includes at least one roll commands,
Methods described includes monitoring step, and this supervision step is to realize for being generated by described flight management system (3a, 3b)
The supervision of data, so as to detecting inconsistent,
It is characterized in that,
- methods described includes data genaration step, this data genaration step be by with described flight management system (3a, 3b)
Different at least one data generating unit (5a, 5b) to calculate roll commands in real time；And
- described supervision step is at least in the case that the data detecting described flight management system (3a, 3b) is inconsistent,
The roll commands realizing being calculated by two flight management systems (3a, 3b) are horizontal with determined by described data genaration step
Shake the comparison between instruction, so as to detecting when necessary and identifying described two flight management systems (3a, 3b)
Among that flight management system out of order.
9. method according to claim 8 it is characterised in that described supervision step at least that:
- calculate the roll commands being calculated by one of described flight management system (3a, 3b) and by described data genaration
The first difference between the corresponding roll commands that unit (5a, 5b) is calculated, and by this first difference and predetermined first
Tolerance limit compares；
- calculate and given birth to by described data by another roll commands being calculated in described flight management system (3a, 3b)
Become the second difference between unit (5a, 5b) the corresponding roll commands that calculated, and by this second difference and described first
Tolerance limit compares；And
- only when one of described first difference and described second difference are more than described first tolerance limit, just determine described corresponding
Yaw instruction be inconsistent, and detect and identify that the flight management system calculating this inconsistent yaw instruction is
Out of order.
10. a kind of aircraft is it is characterised in that it includes flight management assembly according to any one of claim 1 to 7
(1).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1556385A FR3038709B1 (en) | 2015-07-06 | 2015-07-06 | AIRCRAFT FLIGHT MANAGEMENT ASSEMBLY AND METHOD OF MONITORING SUCH AN ASSEMBLY. |
| FR1556385 | 2015-07-06 |
Publications (2)
| Publication Number | Publication Date |
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| CN106340207A true CN106340207A (en) | 2017-01-18 |
| CN106340207B CN106340207B (en) | 2019-04-12 |
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| CN201610529202.4A Active CN106340207B (en) | 2015-07-06 | 2016-07-06 | For aircraft flight management component, monitor the method and aircraft of the component |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US10077119B2 (en) |
| CN (1) | CN106340207B (en) |
| FR (1) | FR3038709B1 (en) |
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| CN111081073A (en) * | 2019-12-27 | 2020-04-28 | 中国航空工业集团公司西安飞机设计研究所 | Method for bidirectional sorting of waypoints of flight management system |
| CN111433612A (en) * | 2017-10-11 | 2020-07-17 | 埃姆普里萨有限公司 | Neural network system for estimating combined training of aircraft aerial data based on model and flight information |
| CN113029146A (en) * | 2021-03-02 | 2021-06-25 | 北京白龙马云行科技有限公司 | Navigation action prediction model training method, navigation action generation method and device |
| CN113646707A (en) * | 2019-04-05 | 2021-11-12 | 赛峰飞机发动机公司 | Device for controlling an aircraft engine comprising two redundant control channels |
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| FR3024229B1 (en) * | 2014-07-23 | 2016-12-09 | Airbus Operations Sas | METHOD AND APPARATUS FOR AUTOMATIC MANAGEMENT OF AIR OPERATIONS REQUIRING A GUARANTEE OF NAVIGATION PERFORMANCE AND GUIDANCE OF AN AIRCRAFT. |
| FR3081580B1 (en) * | 2018-05-25 | 2020-05-22 | Thales | ELECTRONIC METHOD AND DEVICE FOR MANAGING THE DISPLAY OF AN AIRCRAFT FLIGHT PROFILE, COMPUTER PROGRAM AND RELATED ELECTRONIC DISPLAY SYSTEM |
| FR3083337B1 (en) | 2018-07-02 | 2020-09-25 | Airbus Operations Sas | AIRCRAFT FLIGHT MANAGEMENT UNIT AND PROCESS FOR MONITORING SUCH A FLIGHT MANAGEMENT UNIT |
| CN113063443B (en) * | 2021-03-19 | 2023-12-01 | 四川大学 | Flight error real-time assessment method based on actual navigation performance |
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Also Published As
| Publication number | Publication date |
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| CN106340207B (en) | 2019-04-12 |
| US20170008640A1 (en) | 2017-01-12 |
| FR3038709B1 (en) | 2018-07-06 |
| US10077119B2 (en) | 2018-09-18 |
| FR3038709A1 (en) | 2017-01-13 |
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